Nose bullet anti-icing for gas turbine engines

Details Nose bullet anti-icing for gas turbine engines Nose bullet anti-icing for gas turbine engines

1989-04-13

1990-07-17

Stout, Donald E.

Power plants

Combustion products used as motive fluid

With safety device

416 95, F02C 7047

Patent

active

049413171

ABSTRACT:
A flow inducing means 110 for use in an anti-icing system for a nose bullet 10 of a gas turbine engine of the type in which hot gas is caused to flow along the center of a rotating tube 7,62 towards the nose bullet 10 to heat it, and cooled air is centrifuged to the surface of the bore of the tube 7,62 and is displaced rearwardly along the tube. The tube 7,62 is open at its rear end, and the flow inducing means 110 is positioned adjacent the open end. The flow inducing means 110 comprises a plurality of radial vanes 111 which enters in a radially inwards direction and the vanes 111 are shaped and positioned to redirect the gas axially along the center of the tube 7. The flow inducer 110 may include a shroud 115 which has a circumferential inlet opening and an axial facing outlet 116. The shroud may serve as a flow separator which separates the incoming hot gas from the cooled gas exiting the tube.

REFERENCES:
patent: 2618433 (1952-11-01), Loos et al.
patent: 3663118 (1972-05-01), Johnson
patent: 3925979 (1975-12-01), Ziegler
patent: 4485619 (1984-12-01), Moore et al.
patent: 4757963 (1988-07-01), Cole

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